US20210331815A1 - Method for controlling gap distribution of wing-fuselage joining based on measured data - Google Patents

Method for controlling gap distribution of wing-fuselage joining based on measured data Download PDF

Info

Publication number
US20210331815A1
US20210331815A1 US17/169,521 US202117169521A US2021331815A1 US 20210331815 A1 US20210331815 A1 US 20210331815A1 US 202117169521 A US202117169521 A US 202117169521A US 2021331815 A1 US2021331815 A1 US 2021331815A1
Authority
US
United States
Prior art keywords
point
cloud data
gap
point cloud
wing
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Abandoned
Application number
US17/169,521
Other languages
English (en)
Inventor
Jun Wang
Zeyong WEI
Yan Wang
Honghua CHEN
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Nanjing University of Aeronautics and Astronautics
Original Assignee
Nanjing University of Aeronautics and Astronautics
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Nanjing University of Aeronautics and Astronautics filed Critical Nanjing University of Aeronautics and Astronautics
Publication of US20210331815A1 publication Critical patent/US20210331815A1/en
Abandoned legal-status Critical Current

Links

Images

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
    • B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/26—Attaching the wing or tail units or stabilising surfaces
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/10—Geometric CAD
    • G06F30/15—Vehicle, aircraft or watercraft design
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
    • G06F2119/18—Manufacturability analysis or optimisation for manufacturability
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
    • Y02P90/00—Enabling technologies with a potential contribution to greenhouse gas [GHG] emissions mitigation
    • Y02P90/02—Total factory control, e.g. smart factories, flexible manufacturing systems [FMS] or integrated manufacturing systems [IMS]

Definitions

  • the present application relates to aviation manufacturing, and more particularly to a method for controlling a gap distribution of a wing-fuselage connection based on measured data.
  • the size of the jointing gap between the various parts of the aircraft is an important indicator of the quality of the assembly.
  • a method is also provided for selecting multiple parts of the same type to connect with the whole body of the aircraft, and selecting the best part for assembly, which helps to improve an overall assembly quality of the aircraft.
  • An object of the present disclosure is to provide a method for controlling a gap distribution of a wing-fuselage joining based on measured data, which can control the gap distribution of the wing-fuselage joining through feature weights based on the measured data to satisfy the gap requirements during wing fuselage assembly, thereby improving assembly quality and production efficiency of the wing fuselage, and meeting the technical requirements for controlling the gap distribution of the wing-fuselage joining.
  • the present disclosure provides a method for controlling a gap distribution of a wing-fuselage joining based on measured data, comprising:
  • a process of respectively collecting original point cloud data of the wing and original point cloud data of the central wing box of the aircraft in step S 1 comprises:
  • step S 14 by combining with the scanning control field established in step S 12 , performing point cloud refinement on the original point cloud data of the wing fuselage and the original point cloud data of the central wing box to enhance a detailed description.
  • a process of preprocessing the original point cloud data of the wing and the original point cloud data of the central wing box comprises:
  • a process of performing sparsification on the extracted points based on curvature comprises:
  • Q j is an average curvature of a point x j in the point set X i of the neighborhood of the point x i ;
  • a process of respectively registering the preprocessed point cloud data of the wing and the preprocessed point cloud data of the center wing box with the corresponding theoretical models comprises:
  • Q j is an average curvature of a point x j in the point set X i of the neighborhood of the point x i ;
  • a process of respectively registering the preprocessed point cloud data of the wing and the preprocessed point cloud data of the center wing box with the corresponding theoretical models comprises:
  • FIG. 1 is a flowchart of a method for controlling a gap distribution of a wing-fuselage joining based on measured data according to an embodiment of the present disclosure.
  • FIG. 2 is a schematic diagram of pasting code points of the wing according to an embodiment of the present disclosure.
  • FIG. 3 is a schematic diagram of point cloud data of the wing according to an embodiment of the present disclosure.
  • FIG. 4 is a schematic view of a joining surface of a central wing box according to an embodiment of the present disclosure.
  • FIG. 5 is a schematic diagram of a weight distribution of a joining surface area of the wing according to an embodiment of the present disclosure.
  • FIG. 6 is a schematic diagram of a gap between the wing and the central wing box according to an embodiment of the present disclosure.
  • the embodiment provides a method for controlling a gap distribution of a wing-fuselage joining based on measured data, including the following steps.
  • the code points and gauge points are pasted around the joining surface of aircraft wing fuselage respectively, the coordinate information of the code points and gauge points on the wing fuselage are obtained by using a photogrammetry technology to establish a scanning control field. And then the wings and the central wing box are scanned respectively by using the scanner, to obtain the point cloud data. The point cloud data are added to the control field established by photogrammetry, to enhance the detailed description.
  • the pasting of code points is shown in FIG. 2 .
  • the point cloud data obtained by the scanner contains some worthless noise points and outliers, which can be removed by Gaussian filtering.
  • the points that do not belong to the joining surface of the wing and the central wing box are divided by using point cloud segmentation, and only the points belonging to the joining surface of the wing and the central wing box are retained.
  • FIG. 3 shows the point cloud data of the wing after segmentation. Since the scanned point cloud has a high density, it requires a lot of time to directly process the data. Actually, the points on the plane position can be sparser, and the points on the boundary and curvature can be denser, so the point cloud data can be performed sparsification through the curvature.
  • a process of sparsification on the point cloud includes the following steps.
  • a point set of a neighborhood of the point is defined as X i , where x j ⁇ X i ; 1 ⁇ j ⁇ n, n is the number of points in the point set of the neighborhood.
  • An average curvature Q i of the point x i is calculated based on the point set X i of the neighborhood.
  • an average value P i of the average curvature Q i is calculated according to the following formula:
  • Q j is an average curvature of a point x j in the point set X i of the neighborhood of the point x i .
  • a corresponding retention time F and a calculation time S for each of points in the point cloud data is set.
  • step S 224 is repeatedly processed until all points are processed, and a reduction probability ⁇ of each of points is calculated according to the following formula:
  • the reduction probability of a point is greater than or equal to 0.5, the point is retained. If the reduction probability of a point is less than 0.5, the point is deleted.
  • the point cloud data is obtained by scanning with the scanner.
  • the actual data and the ideal model are definitely different, but there is still a certain joining between the two.
  • Operations such as alignment and feature extraction on the model are simpler than those on the point cloud, thus the point cloud data needs to be firstly registered with the model.
  • the point cloud data and the positioning points on the entity model at the same position are firstly extracted.
  • the transformation matrix transformed from the positioning point of the point cloud data to the positioning point of the entity model is calculated by using the SVD algorithm.
  • the point cloud data are transformed by using the transformation matrix.
  • the transformed point cloud data and entity model are registered by using the ICP algorithm.
  • the key features (positioning points and feature points of joining surface) during joining on the entity model are selected.
  • Multiple sets of positioning points on the entity model are mapped to the point cloud data by using the registered point cloud data and the entity model in step S 3 , where each set of positioning points includes a positioning point of the wing and a positioning point of the central wing box, which are provided for joining the point cloud data of the wing and the point cloud data of the central wing box.
  • the point is marked as the feature point of the point cloud data.
  • FIG. 4 is a schematic diagram of the joining surface of the central wing box, and the joining surface can be divided into 4 areas.
  • An objective function F is constructed as follows:
  • S i is the positioning point of the wing
  • H i is the positioning point of the central wing box
  • X is a rotation matrix
  • Z is a translation matrix
  • the corresponding X and Y are obtained by minimizing the objective function.
  • a centroid S′ of the positioning point S i of the wing and a centroid H′ of the positioning point of the central wing box are respectively calculated as follows:
  • any positive definite matrix AA T and an orthogonal matrix B satisfy: Trace(AA T ) ⁇ Trace(BAA T ).
  • step S 5 the weight is subtly adjusted to control the gap distribution according to the gap of the feature points, where the specific steps are as follows.
  • the joining surface is divided into R areas, and the number of feature points in each of the areas is recorded as N, where C max r and C min r are an upper gap tolerance and a lower gap tolerance of the feature point gap of the area r; 1 ⁇ r ⁇ R.
  • the upper and lower gap tolerance and the number of feature points are different in different areas.
  • a gap value at a point in the area r is c rn , where 1 ⁇ n ⁇ N, and C min r ⁇ c rn ⁇ C max r .
  • Feature points having a same weight in a same area are recorded as ⁇ r , where the weight is related to the gap tolerance in the area.
  • ⁇ r 1 / ⁇ r ⁇ 1 R ⁇ 1 / ⁇ r ,
  • FIG. 5 is a schematic diagram of a weight distribution of a joining surface area of the wing.
  • Weight constraints on the two gaps are performed to construct an error function F(X,Z,dX,dZ) as:
  • An optimal pose evaluation model is constructed as:
  • ⁇ i is a weight of the positioning point
  • ⁇ r is a weight of weight gap
  • I is the number of the set of the positioning points
  • R is the number of the areas in the joining surface
  • C max r and C min r are an upper and lower gap tolerance of the feature point gap of the area r.
  • step S 64 If X and Z have no initial value, the X and the Z obtained in step S 5 are adopted. Otherwise, the current X and Z are adopted. And the optimal pose evaluation model is calculated base on the PHR algorithm, to obtain dX and dZ.
  • E is an unit matrix
  • FIG. 6 shows a gap between the wing and the central wing box after subtle adjustment.

Landscapes

  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Geometry (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Theoretical Computer Science (AREA)
  • General Physics & Mathematics (AREA)
  • Manufacturing & Machinery (AREA)
  • Mathematical Optimization (AREA)
  • Mathematical Analysis (AREA)
  • Pure & Applied Mathematics (AREA)
  • Computer Hardware Design (AREA)
  • Evolutionary Computation (AREA)
  • General Engineering & Computer Science (AREA)
  • Computational Mathematics (AREA)
  • Automation & Control Theory (AREA)
  • Transportation (AREA)
  • Mechanical Engineering (AREA)
US17/169,521 2020-04-27 2021-02-07 Method for controlling gap distribution of wing-fuselage joining based on measured data Abandoned US20210331815A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CN202010343957.1A CN111539070B (zh) 2020-04-27 2020-04-27 基于实测数据的翼身对接间隙分布控制方法
CN202010343957.1 2020-04-27

Publications (1)

Publication Number Publication Date
US20210331815A1 true US20210331815A1 (en) 2021-10-28

Family

ID=71980274

Family Applications (1)

Application Number Title Priority Date Filing Date
US17/169,521 Abandoned US20210331815A1 (en) 2020-04-27 2021-02-07 Method for controlling gap distribution of wing-fuselage joining based on measured data

Country Status (2)

Country Link
US (1) US20210331815A1 (zh)
CN (1) CN111539070B (zh)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114648445A (zh) * 2022-03-03 2022-06-21 电子科技大学 一种基于特征点提取及精配准优化的多视角高分辨率点云拼接方法
US11590416B2 (en) * 2018-06-26 2023-02-28 Sony Interactive Entertainment Inc. Multipoint SLAM capture
CN117808703A (zh) * 2024-02-29 2024-04-02 南京航空航天大学 一种多尺度大型部件装配间隙点云滤波方法
EP4372599A1 (en) * 2022-11-18 2024-05-22 The Boeing Company Systems and methods for predictive assembly

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN115630558B (zh) * 2022-12-21 2023-04-14 南京航空航天大学 一种复合材料构件装配变形预测方法
CN116697914B (zh) * 2023-08-04 2023-10-17 南京航空航天大学 一种基于数字孪生的装配间隙实时测量方法

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20030067461A1 (en) * 2001-09-24 2003-04-10 Fletcher G. Yates Methods, apparatus and computer program products that reconstruct surfaces from data point sets
US20190266748A1 (en) * 2018-02-23 2019-08-29 GM Global Technology Operations LLC Crowd-sensed point cloud map

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9068809B1 (en) * 2013-06-06 2015-06-30 The Boeing Company Quasi-virtual locate/drill/shim process
CN103895876B (zh) * 2014-03-27 2015-12-02 浙江大学 基于区域特征引导的机翼壁板和骨架装配间隙的评价方法
CN103901852B (zh) * 2014-03-27 2016-10-05 浙江大学 一种飞机装配结合面数字化加垫方法
US10275565B2 (en) * 2015-11-06 2019-04-30 The Boeing Company Advanced automated process for the wing-to-body join of an aircraft with predictive surface scanning
CN105674904B (zh) * 2016-04-21 2018-09-07 哈尔滨工业大学 一种具有智能化装配特点的汽轮机通流间隙检测方法
CN107687816B (zh) * 2017-08-22 2019-05-14 大连理工大学 一种基于点云局部特征提取的装配间隙的测量方法

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20030067461A1 (en) * 2001-09-24 2003-04-10 Fletcher G. Yates Methods, apparatus and computer program products that reconstruct surfaces from data point sets
US20190266748A1 (en) * 2018-02-23 2019-08-29 GM Global Technology Operations LLC Crowd-sensed point cloud map

Non-Patent Citations (3)

* Cited by examiner, † Cited by third party
Title
D. Brucas , J. S. Visockiene, "Measuring surface geometry of airplane wing by means of two methods", pgs. 44-49 (Year: 2010) *
F. Schmick, N. O. Luders, J. Wollnack, "Automated Assembly of Large CFRP Structures: Adaptive Filling of Joining Gaps with Additive Manufacturing", pgs. 126-132, 2016 (Year: 2016) *
Y. Wang, Y. Liu, H. chen, Q. Xie, K. Zhang, and J. Wang, "Combined Measurement Based Wing-Fuseage Assembly Coordination via multiconstraint Optimization", pgs.1-16, 2022 (Year: 2022) *

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11590416B2 (en) * 2018-06-26 2023-02-28 Sony Interactive Entertainment Inc. Multipoint SLAM capture
CN114648445A (zh) * 2022-03-03 2022-06-21 电子科技大学 一种基于特征点提取及精配准优化的多视角高分辨率点云拼接方法
EP4372599A1 (en) * 2022-11-18 2024-05-22 The Boeing Company Systems and methods for predictive assembly
CN117808703A (zh) * 2024-02-29 2024-04-02 南京航空航天大学 一种多尺度大型部件装配间隙点云滤波方法

Also Published As

Publication number Publication date
CN111539070B (zh) 2022-03-08
CN111539070A (zh) 2020-08-14

Similar Documents

Publication Publication Date Title
US20210331815A1 (en) Method for controlling gap distribution of wing-fuselage joining based on measured data
US11535400B2 (en) Fairing skin repair method based on measured wing data
CN109118574A (zh) 一种基于三维特征提取的快速逆向建模方法
CN112489212A (zh) 一种基于多源遥感数据的建筑物智能化三维测图方法
WO2022099958A1 (zh) 一种基于三维点云坐标的头面部号型分类方法
CN113269791B (zh) 一种基于边缘判定与区域生长的点云分割方法
JP7288870B2 (ja) 画像を生成するシステム
WO2022227486A1 (zh) 一种基于人工智能的遥感田埂界线检测方法、系统、计算机设备及存储介质
CN114419007A (zh) 多策略融合深度学习网络模型的缺陷类型识别方法及系统
CN116721144A (zh) 一种基于点云切片的锥形孔尺寸测量方法
CN117274167A (zh) 一种基于三维信息的成形焊缝外观缺陷提取方法
CN115937226A (zh) 一种基于无人机Lidar点云数据的果树单木分割方法
CN112270746B (zh) 基于邻域协方差特征参数阈值的铝合金3d打印点云精简算法
WO2020164042A1 (zh) 基于边界提取的区域合并图像分割算法
US11543795B2 (en) Airplane structure stiffener repair method based on measured data
CN107507192B (zh) 一种水稻剑叶夹角在体测量便携装置及在体测量方法
CN117893924A (zh) 一种基于树冠形态的无人机激光雷达点云单木分割方法
CN106250687B (zh) 去扁化ipp的沉积砾石圆度计算方法
CN115147433A (zh) 点云配准方法
CN111754461A (zh) 半导体芯片图像字符区域的定位方法、装置
CN108615240B (zh) 一种结合邻域信息与距离权重的非参贝叶斯过分割方法
CA2939304C (en) A pixel-based universal image info extraction models and process flow
CN115049850A (zh) 一种用于肺部ct影像的纤维化区域的特征提取方法
CN113658077A (zh) 一种基于曲率的分区域双边海量点云降噪方法
CN111524098A (zh) 一种基于自组织聚类的神经网络输出层裁剪及模板框尺寸确定方法

Legal Events

Date Code Title Description
STPP Information on status: patent application and granting procedure in general

Free format text: DOCKETED NEW CASE - READY FOR EXAMINATION

STPP Information on status: patent application and granting procedure in general

Free format text: NON FINAL ACTION MAILED

STPP Information on status: patent application and granting procedure in general

Free format text: RESPONSE TO NON-FINAL OFFICE ACTION ENTERED AND FORWARDED TO EXAMINER

STPP Information on status: patent application and granting procedure in general

Free format text: FINAL REJECTION MAILED

STPP Information on status: patent application and granting procedure in general

Free format text: DOCKETED NEW CASE - READY FOR EXAMINATION

STPP Information on status: patent application and granting procedure in general

Free format text: NON FINAL ACTION MAILED

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION